CN1157563C - Burner of gas turbine and its operation method - Google Patents
Burner of gas turbine and its operation method Download PDFInfo
- Publication number
- CN1157563C CN1157563C CNB021080372A CN02108037A CN1157563C CN 1157563 C CN1157563 C CN 1157563C CN B021080372 A CNB021080372 A CN B021080372A CN 02108037 A CN02108037 A CN 02108037A CN 1157563 C CN1157563 C CN 1157563C
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- Prior art keywords
- fuel
- coaxial
- jet
- gas turbine
- combustion chamber
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/36—Supply of different fuels
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
- F23R3/10—Air inlet arrangements for primary air
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/03282—High speed injection of air and/or fuel inducing internal recirculation
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Fluidized-Bed Combustion And Resonant Combustion (AREA)
- Spray-Type Burners (AREA)
Abstract
A gas turbine combustor has a combustion chamber into which fuel and air are supplied, wherein the fuel and the air are supplied into said combustion chamber as a plurality of coaxial jets.
Description
The background technology of invention
Invention field
The present invention relates to gas turbine burner and method of operating thereof.
The explanation of prior art
The present invention be more particularly directed to low NOx type gas turbine burner, this gas turbine burner is discharged the nitrogen oxide of low amount.The prior art is open in the flat 05-172331 of Japanese Patent Application Publication.
In gas turbine burner, because bigger than very, therefore extensively adopt the diffusion combustion system that directly fuel is sprayed in the combustion chamber, so that guarantee that burning is stable in very wide zone from the adjusting that starts to rated load condition.Can also adopt premixed combustion system.
In described prior art, there is the problem of high NOx amount in the diffusion combustion system.Premixed combustion system also has the flameholding when start-up operation and fractional load operation and the problem of flame stabilization, this for example tempering of flameholding problem.In practical operation, preferably address these problems simultaneously.
The invention brief introduction
Main purpose of the present invention provides a kind of gas turbine burner, and the NOx discharge rate of this burner is lower, and combustion stability is good, and the method for operating of this gas turbine burner also is provided simultaneously.
The invention provides a kind of gas turbine burner, combuster, fuel and air supply in this combustion chamber, wherein, fuel and air supply in the described combustion chamber as a large amount of coaxial jets, and each coaxial jet is made up of with the coaxial air-spray of fuel jet a fuel jet and.
And the method for operating of gas turbine burner of the present invention is the method that operation has the gas turbine burner of combustion chamber, and fuel and air supply in this combustion chamber, and wherein, fuel and air supply in the described combustion chamber as a large amount of coaxial jets.
Brief description of drawings
Fig. 1 is the view that comprises the overall cutaway view of representing first embodiment of the invention.
Fig. 2 is the cutaway view of expression diffusion combustion system.
Fig. 3 is the cutaway view of expression premixed combustion system.
Fig. 4 (a) is the cutaway view of the nozzle segment of first embodiment of the invention.
Fig. 4 (b) is the side view of Fig. 4 (a).
Fig. 5 (a) is a cutaway view of representing the nozzle segment of second embodiment of the invention in detail.
Fig. 5 (b) is the side view of Fig. 5 (a).
Fig. 6 (a) is a cutaway view of representing the nozzle segment of third embodiment of the invention in detail.
Fig. 6 (b) is the side view of Fig. 6 (a).
Fig. 7 (a) is a cutaway view of representing the nozzle segment of fourth embodiment of the invention in detail.
Fig. 7 (b) is the side view of Fig. 7 (a).
Fig. 8 (a) is a cutaway view of representing the nozzle segment of fifth embodiment of the invention in detail.
Fig. 8 (b) is the side view of Fig. 8 (a).
Fig. 9 (a) is a cutaway view of representing the nozzle segment of sixth embodiment of the invention in detail.
Fig. 9 (b) is the side view of Fig. 9 (a).
Figure 10 is a cutaway view of representing the nozzle segment of seventh embodiment of the invention in detail.
Figure 11 is a cutaway view of representing the nozzle segment of eighth embodiment of the invention in detail.
The explanation of most preferred embodiment
At first will introduce two kinds of combustion systems of gas turbine burner.
(1) in the diffusion combustion system, as shown in Figure 2, fuel outwards sprays near the air eddy device outlet that is arranged in burner head, thereby intersects with eddy airstream, produces circulation on central shaft, thereby stablizes diffusion flame.
In Fig. 2, the air of being sent by compressor 10 50 is from process between shell body 2 and the combustor liners 3, portion of air flows into combustion chamber 1 as diluent air 32, this diluent air 32 promotes cooling air 31 and combustion gas to mix in combustor liners, and another part air flows into combustion chamber 1 as head vortex air 49 by air eddy device 12.Gaseous fuel 16 outwards sprays into the combustion chamber 1 from diffused fuel nozzle 13, so that intersect with eddy airstream, and forms stable diffusion flame with head vortex air 49 and main combustion air 33.The high-temperature fuel gas that is generated flows into turbine 18 and work done, discharges then.
There is very high combustion stability in the diffusion combustion system here, reaches in the zone of stoichiometric ratio but flame-shaped is formed in the ratio of fuel and oxygen, makes flame temperature be elevated near adiabatic flame temperature.Because when flame temperature raises, the formation speed of nitrogen oxide is pressed index law to be increased, and diffusion combustion is discharged a large amount of nitrogen oxide usually, does not wish like this from control air-polluting aspect.
(2) on the other hand, premixed combustion system is used to reduce the NOx amount.Fig. 3 has represented an example, and wherein, core adopts the good diffusion combustion of combustion stability, and outer circumferential side adopts the low pre-mixing combustion of NOx discharge capacity, to reduce the NOx amount.In Fig. 3, the air of sending from compressor 10 50 is from process between shell body 2 and the combustor liners 3, portion of air flows into combustion chamber 1 as the cooling air 31 that is used for the combustion gas in combustor liners and the combustor liners, and another part air flows into premixing cavity 23 as pre-mixing combustion air 48.Remaining air flows into combustion chamber 1, thereby flows through the passage between premixing cavity 1 passage and the burner end plate, flows through combustion air hole 14 and cooling air hole 17 then.The gaseous fuel 16 that is used for diffusion combustion sprays in the combustion chamber 1 by diffused fuel nozzle 13, thereby forms stable diffusion flame 4.Premixed gas fluid fuel 21 sprays into annular premixing cavity 23 by fuel nozzle 8, thereby mixes with air, so that become premixed air fuel mixture 22.This premixed air fuel mixture 22 flows into combustion chamber 1 to form premixed flame 5.The high-temperature fuel gas that is generated is sent to turbine 18 and work done, discharges then.
But, when adopting this premixed combustion system, the peculiar destabilizing factor of pre-mixing combustion will make flame enter premixing cavity and burn out this structure, perhaps cause producing tempering phenomenon.
In an embodiment of the present invention, fuel injection passages becomes coaxial with the mobile channel arrangement of combustion air, so that formation coaxial jet, wherein, air stream surrounds fuel stream, and the mobile passage of this fuel injection passages and combustion air also is arranged on the wall surface of combustion chamber, so that form the porous coaxial jet, and this porous coaxial jet is arranged to make a large amount of coaxial jet scatterings.And this embodiment is arranged to like this, and promptly part or all coaxial jet can flow into the axis of suitable vortex square ring around burner.And it is arranged to like this, and promptly fuel feed system is divided into a plurality of parts, like this, when this gas turbine start-up operation and fractional load operation, only has the part of this system to carry out the fuel supply.
Surround in the coaxial jet form of fuel at air stream, fuel flows into the combustion chamber, and mixes with on every side coaxial air stream, thereby is formed with the premixed air fuel mixture of appropriate chemical equivalent mixing ratio, and then contacts with high-temperature gas and take fire.Therefore, can carry out low NOx combustion with the lean pre-mixed combustion equivalence.At this moment, the part corresponding with the premixed pipe of common premix burner is very short, and near the fuel concentration wall surface is almost nil, and this feasible generation is owing to the possibility of the burn-out that tempering causes is very little.
And by such structure is provided, promptly part or all coaxial jet flows into around burner axis with suitable vortex square ring, no matter the form of coaxial jet how, can form backflow, simultaneously so that make flame stabilization.
And, by only supplying with fuel when gas turbine start-up operation and the fractional load operation, thereby guarantee flameholding, therefore make that the fuel local concentration is too high by the part of system, and making fuel combustion by the mechanism that is similar to diffusion combustion, this diffusion combustion utilizes the oxygen in the surrounding air.
First embodiment
Introduce the first embodiment of the present invention below with reference to Fig. 1.In Fig. 1, the air of sending from compressor 10 50 is from process between shell body 2 and the combustor liners 3.Portion of air 50 flows into combustion chamber 1 as the cooling air 31 of combustor liners 3.In addition, Sheng Xia air 50 passes through airport 52 inflow combustion chambers 1 as coaxial air from the inside of inner cylinder 2a.
In this embodiment, for fuel 53 and fuel 54, there is the fuel feed system 80 of control valve 80a to be separated out.Just, this fuel feed system 80 is separated into the first fuel feed system 54b and the second fuel feed system 53b.This first fuel feed system 54b and the second fuel feed system 53b have separately controllable control valve 53a and 54a respectively.This control valve 53a and 54a are arranged to like this, and promptly each valve is controlled each fuel flow rate separately according to the load of gas turbine.Wherein, control valve 53a can be controlled at the flow of the fuel nozzle group 56 of core, and control valve 54a can control the flow of fuel nozzle group 55, and this fuel nozzle group 55 is a fuel nozzle group on every side.Present embodiment comprises: a plurality of fuel nozzle groups, a fuel nozzle group and a fuel nozzle group on every side at core; The fuel feed system corresponding with each fuel nozzle group; And control system, this control system can be controlled each fuel flow rate as mentioned above separately.
Introduce nozzle segment in detail below with reference to Fig. 4 (a) and 4 (b).In the present embodiment, the fuel nozzle body is divided into center fuel nozzle 56 and fuel nozzle 55 on every side.In the front side along injection direction of fuel nozzle 55 and 56 corresponding airport 52 and 57 are arranged.The a large amount of airports 52 and 57 that all are minor diameter are on disk shaped part 52a.Provide a large amount of airports 52 and 57, so that corresponding with a large amount of fuel nozzle 55 and 56.
Although the diameter of airport 52 and 57 is very little, but preferably make this hole form such size, promptly when from the fuel of fuel nozzle 55 and 56 ejections through airport 52 with 57 the time, can be accompanied by ambient air and form fuel jet and surround the annular air stream of this fuel jet.For example, preferably this diameter less times greater than from fuel nozzle 55 and 56 the ejection jet diameters.
Airport 52 and 57 is arranged to form coaxial jet with fuel nozzle 55 and 56, and coaxial jet is from the end surfaces ejection of airport 52 and 57 in a large number, and in this coaxial jet, annular air stream surrounds fuel stream.Just, fuel nozzle 55 and 56 teasehole are arranged to airport 52 and 57 coaxial or almost coaxial, and this fuel jet sprays near the import center of airport 52 and 57, thereby make this fuel jet and the stream of annular air on every side form coaxial jet.
Because fuel and air are arranged to form the coaxial jet of a large amount of minor diameters, fuel and air can be in very short distance mixing.Therefore, do not have inappropriate fuel to distribute, and can keep very high efficiency of combustion.
And, because the structure of present embodiment has promoted partly-premixed close of fuel before the end surfaces from airport sprays, therefore can think that this fuel and air can mix in the distance of much shorter.And, by regulating the length of airport passage, can will in this passage, produce the status adjustment of mixing hardly to almost completely premixed state in this passage.
And, in the present embodiment, make center fuel nozzle 56 and center airport 57 that suitable vortex angle be arranged, thereby produce vortex around the combustion chamber axis.By making corresponding airport 57 that the vortex angle be arranged so that produce swirl component, because this vortex can form stable recirculating zone, thereby make flame stabilization in comprising the air fuel mixture stream of center fuel around the combustion chamber axis.
And it is very effective to the various load conditions of gas turbine that present embodiment can be thought.By utilizing control valve 53a and the 54a shown in Fig. 1 to come regulate fuel flow, gas turbine is worked under various load conditions.
Just, under low gas turbine load condition, fuel flow rate is very little with the ratio of total air volume.At this moment, by backbone fuel 53 only, the fuel concentration level in the central area can remain to be higher than and form the required level of the retention flame.And, under high gas turbine load condition,, can totally form oil-poor low NOx combustion by backbone fuel 53 and fuel 54 on every side.And, under middle load condition, be set to greater than 1 by the equivalent ratio of fuel 53 volumes in center with the air volume that flows out from airport 57, can work in the mode that is similar to diffusion combustion, this diffusion combustion utilizes ambient air to burn.
Therefore, according to various gas turbine loads, can make flame stabilization and carry out low NOx combustion.
As mentioned above, surround the coaxial jet of fuel by being arranged to air stream, fuel is the combustion chamber for example, and mixes with on every side coaxial air stream, thereby be formed with the premixed air fuel mixture of appropriate chemical equivalent mixing ratio, what contact with high-temperature gas then takes fire.Therefore, can carry out low NOx combustion with the lean pre-mixed combustion equivalence.At this moment, very short with the corresponding part of premixed pipe of common premix burner.
And near the fuel concentration wall surface is almost nil, and this feasible generation is owing to the possibility of the burn-out that tempering causes is very little.
As mentioned above, present embodiment can provide a kind of gas turbine burner with low NOx discharge rate and good combustion stability, and a kind of method of operating of this gas turbine burner.
Second embodiment
Fig. 5 (a) and 5 (b) have represented the nozzle segment of second embodiment in detail.In this embodiment, single fuel system is arranged, this single combustion system is not separated into core and peripheral part.And, there is not the vortex angle in the nozzle and the combustion air hole of core.When making that owing to operation reason or fuel type combustion stability is inessential, present embodiment can be simplified this nozzle arrangements.
The 3rd embodiment
Fig. 6 (a) and 6 (b) have represented the 3rd embodiment.This embodiment is arranged to like this, and the nozzle of second embodiment is combined to form a burner shown in promptly a plurality of Fig. 5.Just, a plurality of modules are combined to form a burner, and each module is made of fuel nozzle and airport.
As described in first embodiment, this structure can provide a plurality of fuel system, thereby variation that can the handling flexibly turbine loads can also make each burner that different abilities be arranged by the number that increases and reduce nozzle at an easy rate.
The 4th embodiment
Fig. 7 (a) and 7 (b) are depicted as the 4th embodiment.This embodiment is basic identical with second embodiment, and but, distinctive points is for making coaxial jet self that swirl component be arranged by air eddy device 58.
This structure can promote the mixing of each coaxial jet, and this can carry out low NOx combustion more equably.Make fuel jet have the fuel nozzle structure of swirl component also can promote to mix.
The 5th embodiment
Fig. 8 (a) and 8 (b) are depicted as the 5th embodiment.The distinctive points of this embodiment is for replacing being installed in the nozzle on the 3rd embodiment central shaft with common diffusion burner 61, this common diffusion burner 61 comprise air eddy device 63 and respectively with the crossing fuel nozzle hole 62 of this vortice.
In this structure, when startup, acceleration and fractional load, utilize the burner of common diffusion combustion, when startup stability was also important, present embodiment was very favourable.
The 6th embodiment
Fig. 9 (a) and 9 (b) are depicted as the 6th embodiment.This embodiment has liquid fuel nozzle 68 and the injection air nozzle 69 in the diffusion burner 61 of Fig. 8 (a) and 8 (b) illustrated embodiment, and like this, liquid fuel can atomize by injection air 65, thereby carries out liquid fuel combustion.Although consider that from low NOx discharge rate aspect present embodiment is not fine, present embodiment makes that burner can the based on fuel supply condition and flexible working.
The 7th embodiment
Figure 10 shows that the 7th embodiment.This embodiment also provides auxiliary fuel supply-system 71, collector 72 and nozzle 73 in the burner downstream except first embodiment shown in Fig. 1 and Fig. 4 (a) and 4 (b).The fuel that sprays from nozzle 73 flows into the combustion chamber as passing the coaxial jet of airport 74, and promotes combustion reaction by the high-temperature gas that flows out from upstream side.
Although this arrangement makes structural load, it can provide the low-NOx combustor of responsive load more flexibly.
The 8th embodiment
Figure 11 shows that the 8th embodiment.In this embodiment, each fuel nozzle of Fig. 5 (a) and 5 (b) illustrated embodiment is made double structure, and like this, liquid fuel 66 is supplied with internal liquid fuel nozzle 68, and injection air 65 is supplied with external nozzles 81.This structure can form a large amount of coaxial jets when using liquid fuel 66, thereby can realize low NOx combustion under the situation of tempering hardly.
And, replace injection air to supply with by the supply of stop liquid fuel with gaseous fuel, it can also be as the low-NOx combustor of gaseous fuel.Therefore, the burner of a kind of energy treat liquid fuel and gaseous fuel can be provided.
As mentioned above, constitute double structure so that can replace or combined jet liquid fuel and gaseous fuel by making part or all fuel nozzle, thus can treat liquid and gaseous fuel.
Therefore, according to the foregoing description, by being furnished with the coaxial jet of a large amount of air stream encirclement fuel, fuel flows into the combustion chamber, and mix with on every side coaxial air stream, thereby form premixed air fuel mixture, contact with high-temperature gas then and burn with appropriate chemical equivalent mixing ratio.Therefore can be equivalent to the low NOx combustion of lean pre-mixed combustion.At this moment, the part corresponding with the premixed pipe of common premix burner is very short, and near the fuel concentration wall surface is almost nil, and this makes owing to tempering causes that the possibility of burn-out is very low.
Present embodiment can provide a kind of gas turbine burner with low NOx discharge rate and good combustion stability, and the method for operating of this gas turbine burner is provided.
Claims (11)
1. gas turbine burner, combuster, fuel and air supply in this combustion chamber, wherein, fuel and air supply in the described combustion chamber as a large amount of coaxial jets, and each coaxial jet is made up of with the coaxial air-spray of fuel jet a fuel jet and.
2. gas turbine burner, comprise the fuel nozzle that is used to inject fuel in the combustion chamber and be used for air is ejected into shown in airport in the combustion chamber, wherein, this fuel nozzle and airport are arranged to like this, and promptly this fuel and air are ejected in the described combustion chamber as a large amount of coaxial jets.
3. a gas turbine burner comprises fuel nozzle, airport and combustion chamber, and wherein, this this fuel and air are ejected in the described combustion chamber as the coaxial jet of a large amount of minor diameters.
4. gas turbine burner according to claim 3, wherein: the teasehole of fuel nozzle is arranged to coaxial or almost coaxial with airport, fuel jet sprays near airport import center, and fuel jet and the annular air stream that surrounds this fuel jet are ejected in the combustion chamber from the outlet of airport as coaxial jet.
5. gas turbine burner according to claim 4, wherein: a large amount of fuel nozzles is divided into a plurality of fuel feed systems, and control system can be according to the load of gas turbine and is controlled each flow fuel separately.
6. gas turbine burner according to claim 5, wherein: part or all fuel nozzle in a large amount of fuel nozzles and corresponding airport have the vortex angle, and this vortex angle provides the swirl component around burner axis.
7. gas turbine burner according to claim 5, wherein: the teasehole of fuel nozzle is arranged to coaxial or almost coaxial with airport, fuel jet sprays near airport import center, and fuel jet and the annular air stream that surrounds this fuel jet are ejected in the combustion chamber from the outlet of airport as coaxial jet, and
A plurality of modules are combined to form burner, and each module comprises fuel nozzle and airport.
8. according to any one described gas turbine burner in the claim 3 to 7, wherein: have to make each airport or fuel nozzle that the mechanism around the swirl component of each axis be arranged.
9. gas turbine burner according to claim 3, wherein: part or all fuel nozzle constitutes double structure, like this, can replace or combined jet liquid fuel and gaseous fuel.
10. an operation has the method for the gas turbine burner of combustion chamber, fuel and air supply in this combustion chamber, wherein, fuel and air supply in the described combustion chamber as a large amount of coaxial jets, and each coaxial jet is made up of with the coaxial air-spray of fuel jet a fuel jet and.
11. an operation has the method for the gas turbine burner of combustion chamber, fuel and air supply in this combustion chamber, wherein, provide the fuel nozzle that is used for burner oil in a large number, this fuel nozzle is divided into a plurality of fuel feed systems, each flow fuel can be controlled separately according to the load of gas turbine, and this fuel and air are supplied to as a large amount of coaxial jets.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
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JP259119/2001 | 2001-08-29 | ||
JP2001259119 | 2001-08-29 |
Publications (2)
Publication Number | Publication Date |
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CN1401938A CN1401938A (en) | 2003-03-12 |
CN1157563C true CN1157563C (en) | 2004-07-14 |
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Application Number | Title | Priority Date | Filing Date |
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CNB021080372A Expired - Lifetime CN1157563C (en) | 2001-08-29 | 2002-02-28 | Burner of gas turbine and its operation method |
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US (4) | US6813889B2 (en) |
EP (3) | EP1288575B1 (en) |
JP (2) | JP2009079893A (en) |
CN (1) | CN1157563C (en) |
DE (1) | DE60216206T2 (en) |
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2002
- 2002-02-27 US US10/083,360 patent/US6813889B2/en not_active Expired - Lifetime
- 2002-02-28 CN CNB021080372A patent/CN1157563C/en not_active Expired - Lifetime
- 2002-02-28 EP EP02004681A patent/EP1288575B1/en not_active Expired - Lifetime
- 2002-02-28 DE DE60216206T patent/DE60216206T2/en not_active Expired - Lifetime
- 2002-02-28 EP EP07012941.6A patent/EP1843099B1/en not_active Expired - Lifetime
- 2002-02-28 EP EP06003977.3A patent/EP1684016B1/en not_active Expired - Lifetime
-
2003
- 2003-09-10 US US10/658,465 patent/US6912854B2/en not_active Expired - Lifetime
-
2004
- 2004-02-24 US US10/784,216 patent/US7313919B2/en not_active Expired - Lifetime
- 2004-07-28 US US10/900,107 patent/US7117677B2/en not_active Expired - Lifetime
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2009
- 2009-01-23 JP JP2009012467A patent/JP2009079893A/en active Pending
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2010
- 2010-04-16 JP JP2010094596A patent/JP4998581B2/en not_active Expired - Lifetime
Cited By (9)
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CN101858595A (en) * | 2009-04-03 | 2010-10-13 | 株式会社日立制作所 | Combustor and method for modifying the same |
US8763399B2 (en) | 2009-04-03 | 2014-07-01 | Hitachi, Ltd. | Combustor having modified spacing of air blowholes in an air blowhole plate |
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CN103032894A (en) * | 2011-09-28 | 2013-04-10 | 通用电气公司 | System for supplying pressurized fluid to cap assembly of gas turbine combustor |
CN103032894B (en) * | 2011-09-28 | 2016-08-17 | 通用电气公司 | System for the cap assemblies of supplied with pressurised fluid to gas turbine burner |
CN105229379A (en) * | 2013-03-13 | 2016-01-06 | 三菱日立电力系统株式会社 | Gas turbine combustor |
CN105229379B (en) * | 2013-03-13 | 2017-06-13 | 三菱日立电力系统株式会社 | Gas turbine combustor |
US10060625B2 (en) | 2013-03-13 | 2018-08-28 | Mitsubishi Hitachi Power Systems, Ltd. | Gas turbine combustor |
Also Published As
Publication number | Publication date |
---|---|
US6912854B2 (en) | 2005-07-05 |
US6813889B2 (en) | 2004-11-09 |
EP1288575B1 (en) | 2006-11-22 |
US20040045297A1 (en) | 2004-03-11 |
CN1401938A (en) | 2003-03-12 |
EP1684016A1 (en) | 2006-07-26 |
US7313919B2 (en) | 2008-01-01 |
EP1843099A2 (en) | 2007-10-10 |
JP4998581B2 (en) | 2012-08-15 |
EP1288575A3 (en) | 2004-04-21 |
JP2010156350A (en) | 2010-07-15 |
DE60216206T2 (en) | 2007-07-05 |
EP1684016B1 (en) | 2017-09-20 |
US20050000222A1 (en) | 2005-01-06 |
EP1843099A3 (en) | 2015-03-11 |
US7117677B2 (en) | 2006-10-10 |
JP2009079893A (en) | 2009-04-16 |
EP1843099B1 (en) | 2017-09-27 |
US20040011054A1 (en) | 2004-01-22 |
DE60216206D1 (en) | 2007-01-04 |
EP1288575A2 (en) | 2003-03-05 |
US20040163393A1 (en) | 2004-08-26 |
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